Pieces resembling fins were cut out from an old binder and hot glued equidistant
to each other and parallel to the plastic tube. The engine mount was covered with glue
and stuffed inside the plastic tube. The one end of the elastic was glued inside the
plastic tube and the other end was attached to a nose cone shaped from a block of
styrofoam. A parachute cut from a plastic bag and tied with strings was glued to the
elastic. A straw was then glued onto the body tube to accommodate the launching device.
The parachute was powered with talcum, and then stuffed into the body tube.
The entire rocket was then spray-painted.
Launch Procedure:
An engine was placed into the engine mount. An igniter was placed into the clay
nozzle and held in place by an igniter plug. Alligator clips were attached to the igniter.
The rocket was placed on the launchpad, the launch button was then pressed.
ConclusionReturn to top
Our rocket preformed well. It reached a maximum velocity of 39 m/s with an acceleration of
68.42 m/s² and the parachute deployed successfully on both trials, slowing it down to 0.44m/s². Since the parachute was so effective, the rocket stayed intact for the first trial, and it was likely it would stay intact for the second trial. However, since the second trial ended when the rocket landed on the roof of a tall building, its condition is still unknown.
Sources of ErrorReturn to top
The main source of error was the fact that the rocket did not launch perpendicular to the ground
but launched at an angle instead. This means the calculated distance will not be entirely accurate.
Another major source of error was air resistance and wind velocity; simply because it cannot be calculated with the
data we have. This means the values for acceleration during thrust phase, maximum velocity,
and net force on rocket will be higher than what they actually should be.
Purpose
Materials
Procedure
Data
Analysis
Conclusion
Sources of Error
Purpose Return to top
The purpose of this activity was to build and launch a model rocket
and apply concepts learned in class during the entire process.
Materials Return to top
Procedure Return to top
Building Procedure:
Pieces resembling fins were cut out from an old binder and hot glued equidistant
to each other and parallel to the plastic tube. The engine mount was covered with glue
and stuffed inside the plastic tube. The one end of the elastic was glued inside the
plastic tube and the other end was attached to a nose cone shaped from a block of
styrofoam. A parachute cut from a plastic bag and tied with strings was glued to the
elastic. A straw was then glued onto the body tube to accommodate the launching device.
The parachute was powered with talcum, and then stuffed into the body tube.
The entire rocket was then spray-painted.
Launch Procedure:
An engine was placed into the engine mount. An igniter was placed into the clay
nozzle and held in place by an igniter plug. Alligator clips were attached to the igniter.
The rocket was placed on the launchpad, the launch button was then pressed.
Data Return to top
Launch Attempt 1:
(Estes)
Analysis Return to top
5.25N(0.57s) = 0.0768kg(∆v)
2.993Ns = 0.0768∆v
∆v = 38.97 m/s
39.0 m/s = 0 +a (0.57s)
a = 68.42 m/s²
40.5 = 6. 625 V₂
V₂ = 6.02 m/s
a = 0.44m/s
(0.44)(0.0768) – (0.0768)(9.8) = Fair
(0.0338)-(0.753)=Fair
Fair = 0.7188N
Fnet = 0.034N
Conclusion Return to top
Our rocket preformed well. It reached a maximum velocity of 39 m/s with an acceleration of
68.42 m/s² and the parachute deployed successfully on both trials, slowing it down to 0.44m/s².
Since the parachute was so effective, the rocket stayed intact for the first trial, and it was likely
it would stay intact for the second trial. However, since the second trial ended when the rocket
landed on the roof of a tall building, its condition is still unknown.
Sources of Error Return to top
The main source of error was the fact that the rocket did not launch perpendicular to the ground
but launched at an angle instead. This means the calculated distance will not be entirely accurate.
Another major source of error was air resistance and wind velocity; simply because it cannot be calculated with the
data we have. This means the values for acceleration during thrust phase, maximum velocity,
and net force on rocket will be higher than what they actually should be.
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